Modal stability assessment for a morphing aileron subjected to actuation system failures: Numerical analysis supported by test evidence

Arena, Maurizio; Noviello, Maria Chiara; Rea, Francesco; Amoroso, Francesco; Pecora, Rosario; Amendola, Gianluca

doi:10.1109/icmae.2016.7549580

Cited by 8 publications

(5 citation statements)

References 7 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The load-bearing capability of a morphing trailing edge, as well as its ability to reproduce target shapes under the action of aerodynamic and inertial loads, was already discussed in previous works [33,34]. Similar investigations of a more conventional and segmented skin suitable for a morphing aileron were detailed in [35]. Numerical simulations by finite element analysis were elaborated to support these investigations; numerical models' reliability as well as the overall structural concept functionality and performances were finally proven through experimental tests on a full-scale test article.…”

Section: Summary and Investigation Strategymentioning

confidence: 79%

Static and Dynamic Performance of a Morphing Trailing Edge Concept with High-Damping Elastomeric Skin

et al. 2019

Self Cite

View full text Add to dashboard Cite

Nature has many striking examples of adaptive structures: the emulation of birds’ flight is the true challenge of a morphing wing. The integration of increasingly innovative technologies, such as reliable kinematic mechanisms, embedded servo-actuation and smart materials systems, enables us to realize new structural systems fully compatible with the more and more stringent airworthiness requirements. In this paper, the authors describe the characterization of an adaptive structure, representative of a wing trailing edge, consisting of a finger-like rib mechanism with a highly deformable skin, which comprises both soft and stiff parts. The morphing skin is able to follow the trailing edge movement under repeated cycles, while being stiff enough to preserve its shape under aerodynamic loads and adequately pliable to minimize the actuation power required for morphing. In order to properly characterize the system, a mock-up was manufactured whose structural properties, in particular the ability to carry out loads, were also guaranteed by the elastic skin. A numerical sensitivity analysis with respect to the mechanical properties of the multi-segment skin was performed to investigate their influence on the modal response of the whole system. Experimental dynamic tests were then carried out and the obtained results were critically analysed to prove the adequacy of the adopted design approaches as well as to quantify the dissipative (high-damping) effects induced by the rubber foam on the dynamic response of the morphing architecture.

show abstract

Section: Summary and Investigation Strategymentioning

confidence: 79%

Static and Dynamic Performance of a Morphing Trailing Edge Concept with High-Damping Elastomeric Skin

et al. 2019

Self Cite

View full text Add to dashboard Cite

show abstract

“…The ground vibration test (GVT) was carried out in order to validate the dynamic FE model of the morphing aileron. In such manner, a proved finite element model will generate good results for the upcoming aeroelastic analysis (flutter instability) and FHA assessment [31], leading to a safe wind tunnel tests. The structural dynamic response and excitation loads were measured respectively by means of a tri-axial piezoelectric accelerometer, positioned in a characteristic point of the T/A and hence, a load cell connected to the electro-dynamic actuator through a light-weight metallic stringer.…”

Section: Ground Resonance Test and Fe Updatingmentioning

confidence: 99%

Numerical and experimental validation of a full scale servo-actuated morphing aileron model

Arena

Amoroso

Pecora

et al. 2018

Smart Mater. Struct.

Self Cite

View full text Add to dashboard Cite

Aircraft industry is by now deeply involved in technological breakthroughs bringing innovative frameworks, in which the morphing systems constitute the most promising scenario. These systems are taking a remarkable role among the unconventional solutions for the improvement of performance in the operating conditions. The application of morphing devices involves a combination among structural and aerodynamic analyses, actuation requirements, weight assessment and flight control performance. The research project CRIAQ-MDO505, Canadian–European cooperation project on smart technologies, has investigated morphing structures potential through the design and the manufacturing of a variable camber aileron tailored to CS-25 category aircraft applications. This paper is especially focused on the most considerable results able to validate the conceptual design: functionality, ground vibration and wind tunnel tests outcomes have been discussed. The ailerons typically constitute crucial elements for the aerodynamic forces equilibrium of the wing. Therefore, compared to the traditional architectures, the need of studying the dynamic performance and the following aeroelastic impact is, in the specific case of servo-actuated variable-shaped systems, higher. Relying upon the experimental evidence within the present research, the issue appeared concerns the critical importance of considering the dynamic modelling of the actuators in the design phase of a smart device. The higher number of actuators and mechanisms involved makes de facto the morphing structure much more complex. In this context, the action of the actuators has been modelled within the numerical model of the aileron: the comparison between the modal characteristics of numerical predictions and testing activities has shown a high level of correlation. Moreover, the compliance of the device with the design morphing shapes has been proved by wind tunnel test. The outcomes are expected to be key insights for future designers to better comprehend the dynamic response of a morphing aileron, primary knowledge for flutter and failure analyses.

show abstract

“…8) tailored for assessment of its dynamic behavior;  FE model of the morphing aileron ( Fig. 10) characterized by refined mesh specifically conceived for detailed stress analysis (further detail on the model in [13]) and properly updated by means of Ground Vibration Test (GVT) [17]. The complete test article finite-element model was generated in MSC-PATRAN®, and real eigenvalue extraction was performed, according to MSC-NASTRAN® SOL 103 protocol [16], by means of Lanczos Method in the frequency range of interest ([0 Hz; 80 Hz]) with eigenvectors normalized to the maximum value [16].…”

Section: A Structural Modelmentioning

confidence: 99%

Aeroelastic Stability Analysis of a Wind Tunnel Wing Model Equipped with a True Scale Morphing Aileron

Rea¹,

Pecora²,

Amoroso³

et al. 2018

IJMERR

Self Cite

View full text Add to dashboard Cite

In last decades, several research programs were founded worldwide to exploit the potentialities of the morphing concepts, especially to improve aerodynamic efficiency, and so reduce fuel consumption. Among these, the CRIAQ MDO-505 project represents the first joined research program between Canadian and Italian academies, research centers and leading industries. The aim of the project is to design, manufacture and tests in wind tunnel facilities a morphing wing tip for a Bombardier-type aircraft controlled by electric actuators and pressure sensors. In such framework, the authors intensively worked on the flutter clearance demonstration of the wind tunnel wing model equipped with a full-scale variable-camber aileron driven by load-bearing electro-mechanical actuators. Rational approaches were implemented in order to simulate the effects induced by variations of aileron actuator's stiffness on the aeroelastic behavior of the wing. Reliable models were properly implemented to enable fast aeroelastic analyses covering several configuration cases in order to prove clearance from any dynamic instability (flutter) up to 1.2 times the maximum flow speed expected during Wind Tunnel Tests. Finite-element models were properly developed in order to obtain and implement wing model modal parameters (modes shapes, frequencies, generalized masses, damping) in SANDY®, an in-house developed code, that was used for the definition of the coupled aerostructural model as well as for the solution of aeroelastic stability equations by means of theoretical modes association in frequency domain. Obtained results were finally arranged in a diagram showing trend of the flutter speed with respect to changes in control surface harmonic covering a wide range of values for the stiffness of the aileron (external) actuator.  Index Terms-morphing aileron, aeroelasticity, flutter, aeroelastic stability, variable camber, active ribs, smart structures, FEM.I.

show abstract

Modal stability assessment for a morphing aileron subjected to actuation system failures: Numerical analysis supported by test evidence

Cited by 8 publications

References 7 publications

Static and Dynamic Performance of a Morphing Trailing Edge Concept with High-Damping Elastomeric Skin

Static and Dynamic Performance of a Morphing Trailing Edge Concept with High-Damping Elastomeric Skin

Numerical and experimental validation of a full scale servo-actuated morphing aileron model

Aeroelastic Stability Analysis of a Wind Tunnel Wing Model Equipped with a True Scale Morphing Aileron

Contact Info

Product

Resources

About